| Issue |
E3S Web Conf.
Volume 197, 2020
75th National ATI Congress – #7 Clean Energy for all (ATI 2020)
|
|
|---|---|---|
| Article Number | 11009 | |
| Number of page(s) | 9 | |
| Section | Turbomachinery | |
| DOI | https://doi.org/10.1051/e3sconf/202019711009 | |
| Published online | 22 October 2020 | |
Investigation of a Radial Turbines Compatibility for Small Rocket Engine
CIRA Italian Aerospace Research Center, via Maiorise, 81043 Capua (CE), Italy
* Corresponding author: a.leto@cira.it
In the radial turbine preliminary design for an expander rocket engine, a comparison was made with axial turbine used in Pratt & Whitney RL10 engine.
One of the primary requirements of a liquid propellant rocket engine is the generation of a high thrust, which depends on both the mass flow rate of the propellant and the pressure in the thrust chamber.
In expander-cycle engines, which are the subject of the present study, the liquid propellant is first compressed using centrifugal turbo-pumps, then it is used to cool the combustion chamber and the nozzle and, once vaporized, it flows through the turbines used to drive the turbo-pumps.
The aim was to demonstrate the greater efficiency of the radial turbine with a reduction of the pressure ratio with respect to the axial turbine.
© The Authors, published by EDP Sciences, 2020
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